Motor driven propulsor of an aircraft

1. A motor driven propulsor of an aircraft, the motor driven propulsor comprising: magnets disposed in fan shrouds of fan blades connected with a fan hub; a stator having individual conductive coils in a nacelle located radially outside of the fan hub; and a distributed inverter assembly having several inverter power stages and gate drivers, the inverter power stages coupled with the gate drivers and the coils in the stator, wherein the gate drivers are configured to control supply of direct current to the inverter power stages, and the inverter power stages are configured to convert the direct current supplied to the inverter power stages to alternating current that is supplied to the coils in the stator to rotate the magnets and the fan blades around a center line of the fan hub for propelling the aircraft.

2. The motor driven propulsor of claim 1 , wherein the inverter power stages are close coupled with the coils.

3. The motor driven propulsor of claim 1 , wherein the nacelle is configured to transfer heat generated in the coils of the stator over a large surface area that is outside of the fan blades and the fan hub.

4. The motor driven propulsor of claim 1 , wherein the coils of the stator and the inverter power stages are thermally coupled with a radially inward surface of the nacelle and with a radially outward surface of the nacelle.

5. The motor driven propulsor of claim 1 , wherein the inverter power stages and the gate drivers are coupled with a direct current bus, and the inverter power stages, the gate drivers, and the direct current bus are located within the nacelle.

6. The motor driven propulsor of claim 1 , wherein the gate drivers are connected to a common positive direct current bus, a common negative direct current bus, and a common neutral bus.

7. The motor driven propulsor of claim 1 , wherein the magnets are disposed within the fan shrouds of the fan blades in locations that are radially inside of an inner surface of the nacelle.

8. The motor driven propulsor of claim 1 , wherein the nacelle includes a channel that extends around the center line of the fan hub, and wherein the magnets are located in radial protrusions of the fan shrouds that radially project away from the center line of the fan hub and into the channel in the nacelle.

9. The motor driven propulsor of claim 8 , wherein the conductive coils in the stator are located on opposite sides of the channel in the nacelle.

10. The motor driven propulsor of claim 1 , wherein the nacelle includes channels that extend around the center line of the fan hub, and wherein the magnets are located in radial protrusions of the fan shrouds that radially project away from the center line of the fan hub and into the channels in the nacelle.

11. The motor driven propulsor of claim 10 , wherein the conductive coils in the stator are located between the channels in the nacelle.

12. The motor driven propulsor of claim 1 , wherein the inverter power stages are connected with the gate drivers by optical fibers and the gate drivers are configured to control supply of the direct current to the inverter power stages using control signals communicated via the optical fibers.

13. A method for providing a motor driven propulsor of an aircraft, the method comprising: placing magnets disposed in fan shrouds of fan blades connected with a fan hub; positioning a stator having individual conductive coils in a nacelle located radially outside of the fan hub; coupling several inverter power stages of a distributed inverter assembly with several gate drivers, the inverter power stages coupled with the gate drivers; conductively coupling the inverter power stages with the coils in the stator, wherein the gate drivers are coupled with the inverter power stages to control supply of direct current to the inverter power stages, and the inverter power stages are coupled with the gate drivers and the coils to convert the direct current supplied to the inverter power stages to alternating current that is supplied to the coils in the stator to rotate the magnets and the fan blades around a center line of the fan hub for propelling the aircraft.

14. The method of claim 13 , wherein conductively coupling the inverter power stages with the coils includes close coupling the inverter power stages with the coils.

15. The method of claim 13 , wherein the coils of the stator are positioned in the nacelle and the inverter power stages are coupled with the coils such that the coils and the inverter power stages are thermally coupled with a radially inward surface of the nacelle and with a radially outward surface of the nacelle.

16. The method of claim 13 , further comprising: coupling the inverter power stages and the gate drivers with a direct current bus such that the inverter power stages, the gate drivers, and the direct current bus are located within the nacelle.

17. The method of claim 13 , wherein the nacelle includes one or more channels that extend around the center line of the fan hub, and wherein the magnets are positioned in radial protrusions of the fan shrouds that radially project away from the center line of the fan hub and into the one or more channels in the nacelle.

18. The method of claim 13 , wherein the inverter power stages are coupled with the gate drivers by optical fibers.

19. A motor driven propulsor comprising: magnets disposed in fan shrouds of fan blades connected with a fan hub; a stator having individual conductive coils in a nacelle located radially outside of the fan hub; and a distributed inverter assembly having several inverter power stages, the inverter power stages close coupled with the coils in the stator, wherein the inverter power stages are configured to power the corresponding coil in the stator to rotate the magnets and the fan blades around a center line of the fan hub for generating a propulsive force, and wherein the inverter power stages are coupled with the coils in the stator such that one or more inverter power stages continue powering the coils to continue generating the propulsive force after failure of at least one of the inverter power stages.

20. The motor driven propulsor of claim 19 , wherein the coils of the stator and the inverter power stages are thermally coupled with a radially inward surface of an aircraft nacelle and with a radially outward surface of the nacelle.